Sighting means for missiles

ABSTRACT

1. A SIGHTING DEVICE FOR USE IN COMBINATION WITH A COMPUTER FOR PROGRAMMING THE FLIGHTS OF A BATTERY OF GUIDED MISSILES WITH A PLURALITY OF LAUNCHING POINTS DISPLACED FROM THE POSITION OF THE SIGHTING DEVICE, COMPRISING IN COMBINATION A VISUAL SIGHT MOUNTED ON A VERTICAL SIGHTING SHAFT JOURNALLED IN A FIXED SUPPORT FOR ROTATION OF THE SIGHT ABOUT THE VERTICAL SHAFT AXIS, A PLURALITY OF GANGED ROTARY ELECTRICAL POTENTIOMETERS RESPECTIVELY ASSOCIATED WITH THE LAUNCHING POINTS AND MOUNTED ONE ABOVE THE OTHER COAXIALLY WITH THE VERTICAL SIGHTING SHAFT, HAVING ROTORS OF ALL THE POTENTIOMETERS CONNECTED TO THE SIGHTING SHAFT FOR ROTATION THEREWITH IN UNISON, AND HAVING THE BODIES OF THE POTENTIOMETERS MOUNTED ONE ABOVE ANOTHER COAXIALLY WITH THE SIGHTING SHAFT TO ROTATE THEREWITH BY FRICTIONAL ENGAGEMENT OF THE ROTORS WITH THE BODIES, INDEPENDENTLY ACTUABLE FRICTIONAL CLAMPING MEANS TO CLAMP THE BODY OF EACH POTENTIOMETER SELECTIVELY IN A PRESET ANGULAR POSITION WHILE ITS ROTOR ROTATES WITH THE SIGHTING SHAFT, SAID INDEPENDENTLY ACTUABLE FRICTIONAL CLAMPING MEANS COMPRISING A RELEASABLE FRICTION BRAKE ACTING BETWEEN EACH POTENTIOMETER BODY AND THE FIXED SUPPORT, THE BRAKE WHEN ENGAGED HOLDING THE BODY IN A GIVEN ANGULAR POSITION AGAINST ROTATION RELATIVE TO THE SUPPORT, AND A SEPARATE AND INDEPENDENTLY-OPERABLE MOTOR MEANS ASSOCIATED WITH EACH FRICTION BRAKE AND OPERABLE TO ENGAGE AND RELEASE SAID BRAKE, A SEPARATE FRICTION BRAKE IN PERMANENT BUT SLIPPABLE ENGAGEMENT BETWEEN EACH POTENTIOMETER BODY AND THE SAID SIGHTING SHAFT TO AUGMENT THE FRICTIONAL TORQUE TRANSMISSIBLE BETWEEN THE SHAFT AND THE BODY OF THE POTENTIOMETER VIA ITS ROTOR, EACH SAID SEPARATE FRICTION BRAKE CAUSING ITS ASSOCIATED POTENTIOMETER BODY TO ROTATE WITH THE SHAFT WHEN THE ASSOCIATED RELEASABLE FRICTION BRAKE IS DISENGAGED, A STOP MEMBER ON EACH POTENTIOMETER BODY AND A CO-OPERATING ABUTMENT ON THE FIXED SUPPORT ARRANGED TO BE ENGAGED BY THE STOP MEMBER TO LIMIT THE ANGULAR ROTATION OF EACH POTENTIOMETER AT AN EXTREME DATUM POSITION, AND ELECTRIC CIRCUIT MEANS CONNECTED WITH SAID POTENTIOMETERS TO SUPPLY PROGRAMMING INFORMATION TO THE COMPUTER FOR EFFECTING AUTOMATIC PARALLAX CORRECTIONS FOR RESPECTIVE LAUNCHING POINTS RESPONSIVE TO THE POSITION OF THE SIGHTING SHAFT.

March 20, 1973 5. FORD ET AL 3,721,420

SIGHTING MEANS FOR MISSILES Filed Aug. 1, 1962 4 Sheets-Sheet 1 lNvENToRs BRIAN Foam MALcoLm CLAPP /0%; w, vw

ATTORNEYS 4 Sheets-Sheet.

Filed Aug.

INVENTOQS BRIAN oam MALCOLM CLRPP BY m March 20, 1973 Filed Aug. 1 1962 B. FORD ET AL 3,721,420

SIGHTING MEANS FOR MISSILES 4 Sheets-Sheet 1'.

INVENTOIZS BRIAN FORD MALCOLM CLAPP ATTORNEYj United States Patent US. Cl. 244-311 4 Claims This invention relates to sighting means for batteries of guided missiles, and is concerned with providing a battery of missiles with an optical sighting means capable of being angularly zeroed in advance with respect to each missile of the battery in readiness for subsequent use in programming the missiles on to a target at which the sight is aimed.

According to the present invention a sighting device for use in combination with a computer for programming the flights of a battery of guided missiles whose launching points are displaced from the position of the sighting device, comprises a sight mounted for rotation about a vertical axis relative to a support, angular zeroingmeans for measuring and storing the angular bearing of each launching point as sighted in turn from the device by means of the sight, and output means co-operating with the zeroing means to produce or control automatically several output signals associated respectively with the various missiles for feeding into the computer in accordance with the bearing of a target at which the sight of the device is aimed, each of which output signals represents quantitatively a function of the difference between the angular bearing of the target as measured by means of the sight and that of one of the missile launching points as recorded by the zeroing means.

The output signals from the sighting device are supplied to the input of the computer which utilizes this information to calculate the command signals required for programming the missile in accordance with a predetermined flight programme, and supplies the necessary command signals to the missile launching points for transmission to the missiles.

Preferably the device includes means for modifying the output signals in correspondence respectively with the distances of the missile launching points from the position of the sighting device, so that the information supplied to the computer automatically takes account not only of the bearing of each launching point from the control point where the sighting device is located, but also of the distance of each launching point from that control point.

Thus in one form of the present invention a sighting device for use in combination with a computer for programming the flights of a battery of guided missiles whose launching points are displaced from the position of the sighting device, comprises a sight mounted for rotation about a vertical axis relative to a support, a stack of adjustable electrical pick-off devices, each having a moving member movable relative to a body and providing an electrical output quantity dependent on the relative position of its moving member to its body, the moving members of all the pick-off devices being coupled to the sight for movement in response to angular movement thereof, and clamping means associated with each pick-off device whereby the body of the pick-off device is selectively either held fixed to the support in a given position or is freed from the support and coupled to the moving member for movement therewith.

The electrical pick-off devices preferably comprise rotary sine potentiometers, whose associated electrical quantities comprise output voltages proportional to the sines or cosines of the angular settings of the potentiometer rotors relative to the casings.

Preferably each sine potentiometer also has associated with it an over-riding zeroing device for varying the output voltage or voltages of each potentiometer in proportron to the distance of the associated launching point from the sighting device. Such a zeroing device, which may conveniently comprise a linear potentiometer, scales the output voltage of the sine potentiometer up or down in direct proportion to the oifset distance. Thus if each sine potentiometer is provided with two adjustable tappings one comprising a sine tapping and the other comprising a cosine tapping, as well as a linear potentiometer connected in series with it, the output voltages of the potentiometer can provide signals directly representing the co-ordinates of the associated launching points, one of which axes is directed towards the target and the other of which is directed at right angles thereto.

In a convenient construction of the sighting device, the potentiometers are all stacked with their rotors which carry their wiper contacts mounted coaxially on a common vertical shaft coupled coaxially to the sight, and with their casings provided with frictional clamping means by which they may be clamped selectively either to the fixed support of the device or to their associated rotors.

For example the clamping means for each potentiometer may comprise a releasable friction brake acting between the support and the casing of the potentiometer, and a friction coupling in permanent slippable engagement between the potentiometer casing and its rotor.

The stack of potentiometers may include an additional linear potentiometer whose rotor is coupled to the sight and whose casing is permanently secured to the support.

The invention may be carried into practice in various ways, but one specific embodiment will now be described by way of example with reference to the accompanying drawings, in which:

FIG. 1 is a diagram of a typical layout of ground installation for controlling the launching of three missiles from their separated launching points,

FIG. 2 is a perspective view of the upper part of a sighting device used for programming the missiles onto a target,

FIG. 3 is a half-section taken in a vertical plane through the intersecting vertical and horizontal pivotal axes of the upper part of the sighting device of FIG. 2,

FIG. 4 is a section through the upper part of the device of FIGS. 2 and 3, taken in a vertical plane through the vertical pivotal axis at right angles to the plane of section of FIG. 3,

FIG. 5 is a detail perspective view of the potentiometer stack housed in the lower part of the sighting device of FIGS. 2 to 4,

FIG. 6 is a circuit diagram of the potentiometer stack of FIG. 5, and

FIG. 7 is a block diagram of the whole ground installation.

In the illustrated embodiment a battery of three groundto-ground guided missiles, of the type controlled by electrical signals transmitted from its launching point to the missile while in flight through electrical leads trailed behind the fiying missile, is provided with a guidance system including a computer from which command signals are transmitted to the launching points and thence to the missiles in accordance with information fed into the computer from a sighting device arranged to be aimed at a target by the operator. As seen in FIG. 1, the three launching points L L and L of the missiles are distributed to one side of the control point C where the sighting device is located, at respective offset distances s s and .9 The three missiles M M and M are set up on their launching points all initially pointing in the same direction, i.e. parallel to a datum direction indicated by the line C-D in FIG. 1. The angular bearings of the three launching points L L and L as viewed from the control point C are a a and a measured clockwise from the datum direction C-D. In FIG. 1 the line C-T represents the direction from the control point C to a target T appearing generally in front of the control point, onto which target it is desired to programme the missiles. Let the bearing of the target T with respect to the datum line C-D be X.

In order to program the missiles onto the target T, it is necessary to feed into the computer information as to the position of the launching point of each missile relative to the target axis C-T, and this is conveniently done in terms of coordinates measured along and at right angles to the target axis. Thus taking the target axis as the X-axis, and the control point C as the origin, the coordinates of the launching point L are:

1= 1 COS t-X) 1= 1 Sin i-" The coordinates of L are:

Y =S sin (a and the coordinates of L are:

3= 3 Sin rm) For determining the coordinates X X X and Y Y Y automatically and feeding them to the computer the sighting device illustrated in FIGS. 2 to 6 is employed. The device 10 comprises a rotary sight 11 mounted on a support cabinet 12 containing a stack of ganged potentiometers P P P and P The rotary sight 11 comprises a casing 13 formed in two halves 14 which are mounted on a horizontal shaft 15 journalled in bearings 16 carried by brackets 17 mounted on a turntable 18. The turntable 18 is rotatably supported in a bearing ring 19 formed with an inwardly-facing circumferential groove 20 in which the edge of the turntable 18 is engaged. Thus the whole assembly of the sight 11, its casing 13 and its horizontal pivot shaft 15 can be rotated together with the turntable 18 about the vertical axis of rotation 21 of the latter, while the sight in its casing can also be rotated by means of the shaft 15 about the horizontal axis of the latter. The bearing ring 19 is provided with an angular bearing scale 22 and a pointer 23 on the turntable cooperates with the scale 22. Two hand grips 24 and 25 depend respectively from the outer ends of the shaft 15 for use by the operator in controlling the sight. The hand grip 24 is in the form of a rotary twist grip used as a missile selector switch for operating a pair of ganged missile selectors referred to below in connection With FIG. 7. Above the missile selector twist grip 24 is mounted a firing switch 26 for firing a missile selected by the setting of the twist grip 24. Mounted above the other hand grip 25 is a small joystick or manual control lever 27 used for transmitting secondary pitch and yaw command signals to a missile during the latter part of its flight to home it visually onto the target. A bubble-type level 28 is mounted on the upper part of the support cabinet 12.

The two-part casing 13 of the sight 11 containsan optical sighting system which comprises binocular eyepieces 30, two reflective prisms 31 and 32, and a pair of ob ject-glass lenses 33, and a suitable cross-wire or graticule (not shown) is incorporated in the optical system so that the whole sight can be aimed by rotating it about the axes of the shaft 15 and turntable 18 until the cross-wire is aligned with the image of the target T as viewed through the eyepieces 30. The line of sight from the target through the optical system to the eyepieces is indicated by the chain line 35 in FIG. 4.

Each half shell 14 of the sight casing 12 is rigidly secured to the shaft 15, which has splined portions 36 by which the shells 14 are keyed to the shaft so that the sight 11 can be rotated relative to the support cabinet 12 about the horizontal axis of the shaft 15 simply by turning the shaft itself by means of the hand grips 24 and 25 about its longitudinal axis. The sight 11 can also be rotated bodily about the vertical axis 21 relative to the support cabinet 12, by turning the shaft 15 about that axis by means of the hand grips 24 and 25. Such rotary movement of the sight 11 about the vertical axis 21 is transmitted to the rotors of the stack of four potentiometers P P P and P mounted one above another in the support cabinet 12. For this purpose a vertical shaft 37 extends down from the interior of the sight casing 13 into the support cabinet 12 and carries at its upper end a bearing sleeve 38 which embraces the horizontal shaft 15, being retained between spaced washers 39 by securing pins 40. The upper end of the rotor spindle 41 of the uppermost potentiometer P is coupled coaxially to the lower end of the shaft 37 by means of a coupling sleeve 42, and the upper end of the rotor spindle 41 of the next lower potentiometer P is coupled by means of a similar coupling sleeve 42 to the lower end of the rotor spindle of the potentiometer P The two lower potentiometers P and P have their rotor spindles similarly coupled so that in effect the rotors of the four potentiometers P P P and P are mounted on a common shaft for rotation in unison about the axis 21 in accordance with the rotation of the sight 11 about that axis.

The casings 44 of the three uppermost potentiometers P P and P are in light frictional engagement with the respective rotor spindles 41 of the potentiometers so that each casing 44 Will rotate in company with its associated rotor about the vertical axis 21 unless restrained by external means. Such restraint may be selectively provided for each of the three uppermost potentiometers by means of three solenoid-actuated brakes 45 mounted in the support cabinet 12, each carrying a brake shoe 46 on its plunger 47 which is normally spring-pressed into braking engagement with the associated potentiometer casing 44, as shown in FIG. 5 in respect of the upper two potentiometers P and P but is capable of being retracted by the energization of the associated solenoid so that it is clear of the potentiometer casing as shown in FIG. 5 in respect of the potentiometer P whereby the casing is free to rotate with the rotor and the shaft 37. The casing 44 of the lowermost potentiometer P is fixed to the support cabinet 12 and it is therefore not provided with an electromagnetic brake. The angular extent of the rotation of the casings 44 of the potentiometer P to P when their brakes 45 are retracted is further limited by means of radial stops 48 protruding outwardly from the casings and arranged to engage a fixed stop bar 49 mounted in the support cabinet 12. The stop bar 49 can be retracted until it is laterally clear of the stops 48 if required against the action of springs 50 which tend to hold it in its operative position.

The light frictional engagement between the rotor of each of the three potentiometers P and P and its casing 44 is provided by means of a simple friction brake, comprising a disc 52 keyed to the rotor spindle 41 and lightly spring-pressed against the upper surface 53 of the potentiometer casing 44 by means of a spring 54 in the form of a resilient spider. The spring 54 acts between the lower end of the adjacent coupling sleeve 42 and the brake disc 52.

Thus the sighting device may be zeroed in to measure and store particulars of the bearings a a and a of the three launching points L L and L;,, as follows. Initially the sight is lined up to point in the datum direction C-D, with the three potentiometers P P and P set to their zero positions in which the radial stops 48 are in engagement with the stop bar 49 and the turntable pointer 23 is aligned with the zero point of the bearing ring scale 22. The solenoids of the electromagnetic brakes 45 of all three potentiometers P to P are energised to retract the brake shoes so that the casing 44 of each potentiometer P to P is free to turn with the potentiometer rotor, which carries the wiping contacts, under the light frictional torque transmitted by the brake disc 52 to the casing. The sight is slowly rotated about the vertical axis 21 from the datum line and is aimed at the launching points L L and L of the three missiles in turn. When the sight is aimed directly at each in turn of the launching points, the solenoid brake 54 of the associated potentiometer is then de-energized by selector means controlled by the twist grip 24 to cause the brake 45 to be applied by its associated spring and so to clamp the casing 44 of the potentiometer relatively to the support cabinet 12 in its new angular setting corresponding to the angular bearing of the associated launching point as measured from the datum direction. When all three launching points have been traversed in this way and the associated potentiometer casings clamped by the brakes 45 in their corresponding settings, the sight 11 is turned back to point in the datum direction, the potentiometer casings 44 remaining clamped in their individual settings. In this way the three potentiometers P P and P store a set of datum angles respectively equal to the bearing angles a a and a of the three missile launching points from the control. When a target appears in the target area, the sight is aimed at the target by the operator, using the hand grips 24 and 25, and the resultant rotation of the sight 11 on the turn-table 18 about the vertical axis 21 of the latter causes the shaft 37 to rotate the four potentiometer spindles 41 and the rotors of the four po tentiometers P P P and P through the angle corresponding to the bearing X of the target direction C-T with respect to the datum direction C-D. In their new positions the three upper potentiometers P P and P will thus be adjusted to angular settings corresponding to the difference between the angular bearing a a or a of the associating launching point and the bearing X of the target. These potentiometer settings represent quantities which take into account both the target bearing and the bearings of the three launching points with respect to the control point C, and this information can be fed to the computer.

The lowermost potentiometer P whose casing is fixed is used to measure the actual bearing X of the target, and supplies this information directly to the computer.

The circuit arrangements of the four potentiometers are indicated in FIG. 6. The potentiometers P P and P are sine potentiometers. Thus the potentiometer P is provided with a winding 60 formed in two similar parts 60A and 60B connected together in series and earthed at their outer ends and at their junction. The two winding parts 60A and 60B are wound in sine form, and each is provided with a central voltage tapping 61 to which voltage is applied. The potentiometer is provided with two output tappings 62 and 63 mounted on its rotor arm (indicated diagrammatically at 43), whereby the output voltage at the wiper contact 62 corresponds to the cosine of the angular setting of the potentiometer rotor relative to the casing 44, whilst the output voltage of the other wiper contact 63 corresponds to the sine of the angular setting of the potentiometer rotor.

In order that the components X Y of each launching point L related to the target direction C-T can be directly derived from the potentiometer P the input voltage applied to each of the voltage tappings 61 of the potentiometer winding 60 is regulated by a manuallycontrolled linear potentiometer 66 mounted in the top of the support cabinet 12 and provided with a control knob 67 which cooperates with a distance scale 68 calibrated in yards or metres (see FIG. 2). Thus the offset distance s of the launching point L from the control point C can be zeroed into the sighting device by adjusting the linear potentiometer 66 so that its control knob reads off this distance s on the scale, whereby the input voltage supplied to the sine potentiometer P will be scaled down in direct proportion to the offset distance s As a result of this, the output voltages taken from the wiper contacts 62 and 63 of the potentiometer represent directly the components X =s cos (a and Y =s sin (a The other two sine potentiometers P and P are arranged in precisely the same way as the potentiometer P The fourth potentiometer P has a linear winding 69 mounted in its fixed casing and provided with a central earth point and positive and negative voltages applied to its ends. The single wiper contact 70 of the potentiometer P picks off a potential directly equivalent to the target bearing FIG. 7 showsin block diagram form how the sighting device 10 is integrated with the remaining ground equip ment for launching the missiles. The three missiles M M and M are shown on their launching sites L L and L The information provided by the sighting device 10 is supplied to the inputs of a computer, which comprises a pitch programme generator and a yaw programme generator 81. The pitch and yaw command signals from the programme generators 80 and 81 are supplied to one missile selector 82 which is operated by the twist grip selector switch 24. The second missile selector 83 is ganged to the selector 82 for operation therewith by the twist grip selector switch 24, and serves to select the potentiometer P P or P associated with the launching point of the selected missile M M and M and to supply the output signal from the selected potentiometer in the form of the components Xn and Yn through leads 84 and 85 respectively to the pitch programme generator 80 and to the inputs of both generators 80 and 81. The fourth potentiometer P whose casing 44 is fixed, has its output signal supplied directly to the input of the yaw programme generator 81 through a lead 86. Other inputs are supplied to the two programme generators 80 and 81; thus a further linear potentiometer 87 supplies a signal derived from the Yn component and modified in accordance with the cross-slope component of the missile launching points, for example relative to the slope of the ground or of a vehicle on which the missile launching point is positioned or mounted. The linear potentiometer 87 is supplied with the original reference signal R direct and its output, modified in accordance with the crossslope component o, is supplied to the input of the yaw programme generator programme 81. The joystick 27 which is supplied with the reference signal R provides pitch and yaw output signals which are supplied respectively to the pitch and yaw programme generators. In addition a signal corresponding to target elevation 6s is supplied from a further linear potentiometer 88 to the input of the pitch programme generator only, the potentiometer 88 being operated by the horizontal pivot shaft 15 of the sight 11.

The firing of the selected missile is effected by the firing switch 26 under the control of a series-connected standby switch 89, which is also employed to activate the missile selector switch 24.

The sighting device 10 thus provides a simple and straightforward sighting means which can be zeroed in with respect to the launching points when the ground installation is set up in advance of action, and which will store the zeroed in launching point bearings so that when a target appears and is aimed at through the sight 11, the sighting device provides the required information as to the elevation and bearing of the target, automatically related to the offset distances and bearings of the various missile launching points from the control point C, so that the programme generators of the computer can respond to this information and can send the required command signals for programming the flying missile on to the target.

The ground control equipment described and illustrated including the sighting device will be fully automatic in use and once the initial setting up and zeroing in of the launching points has been carried out, on the appearance of a target the operator will only have to close the standby switch 89, select a missile by means of the twist grip switch 24, aim the sight 11 onto the target, and fire. The final homing of each missile on to the target is done visually by the operator who holds the target in view in the sight 11 Whilst operating the joy-stick 27 to supply homing command signals to the missile through its trailing leads.

It will be understood that whereas in the present embodiment only three missiles and three missile launching points are shown, equivalent apparatus can be similarly employed for a battery of any convenient number of missiles, and for this purpose would be provided with a corresponding number of sine potentiometers P P etc. each with its associated offset distance potentiometer 66 and solenoid brake 45.

What We claim as our invention and desire to secure by Letters Patent is:

1. A sighting device for use in combination with a computer for programming the flights of a battery of guided missiles with a plurality of launching points displaced from the position of the sighting device, comprising in combination a visual sight mounted on a vertical sighting shaft journalled in a fixed support for rotation of the sight about the vertical shaft axis, a plurality of ganged rotary electrical potentiometers respectively associated with the launching points and mounted one above the other coaxially with the vertical sighting shaft, having rotors of all the potentiometers connected to the sighting shaft for rotation therewith in unison, and having the bodies of the potentiometers mounted one above another coaxially with the sighting shaft to rotate therewith by frictional engagement of the rotors with the bodies, independently actuable frictional clamping means to clamp the body of each potentiometer selectively in a preset angular position while its rotor rotates with the sighting shaft, said independently actuable frictional clamping means comprising a releasable friction brake acting between each potentiometer body and the fixed support, the brake when engaged holding the body in a given angular position against rotation relative to the support, and a separate and independently-operable motor means associated with each friction brake and operable to engage and release said brake, a separate friction brake in permanent but slippable engagement between each potentiometer body and the said sighting shaft to augment the frictional torque transmissible between the shaft and the body of the potentiometer via its rotor, each said separate friction brake causing its associated potentiometer body to rotate with the shaft when the associated releasable friction brake is disengaged, a stop member on each potentiometer body and a co-operating abutment on the fixed support arranged to be engaged by the stop member to limit the angular rotation of each potentiometer at an extreme datum position, and electric circuit means connected with said potentiometers to supply programming information to the computer for effecting automatic parallax corrections for respective launching points responsive to the position of the sighting shaft.

2. A sighting device as claimed in claim 1 characterized in that each potentiometer is a sine potentiometer whose associated electrical quantity comprises an output voltage proportional to the sine or cosine of the angular setting of the potentiometer rotor relatively to its body.

3. A sighting device as claimed in claim 2 characterized in that each potentiometer rotor carries two wiping contacts, one of which picks off the voltage proportional to the sine of the potentiometer rotor setting relatively to the body, and the other of which picks off the voltage proportional to the cosine of the rotor setting.

4. A sighting device as claimed in claim 1 characterized by a separately-adjustable linear potentiometer electrically connected in series with each potentiometer to constitute an over-riding zeroing means.

References Cited UNITED STATES PATENTS 1,249,274 12/1917 Chandler 1023 X 2,971,437 2/1961 Surtees 24414 X 3,043,197 7/1962 Piper et al 24414 X 2,657,295 10/1953 Barclay 32379 X 2,862,176 11/1958 Lustig 323-79 X 2,971,174 2/1961 Lyon 338-131 X FOREIGN PATENTS 473,523 5/1951 Canada 24414 BENJAMIN A. BORCHELT, Primary Examiner T. H. WEBB, Assistant Examiner US. Cl. X.R. 338131, 134 

